Epoxy composite propellant, preparation method and application thereof

A propellant, epoxy-based technology, applied in offensive equipment, ammonium perchlorate composition, non-explosive/non-thermal agent components, etc., can solve the problem of low fuel cost, easy deformation, and difficult to prepare and process double-base propellants And other issues

Inactive Publication Date: 2021-04-23
石仲仑 +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the composite propellant is soft and easily deformed under high overload conditions, so it is necessary to add support structures to prevent deformation
[0005] In the laboratory design stage of small and medium-sized solid rocket motors, it is difficult to prepare and process standard double-base propellants to meet experimental requirements, and the characteristics of

Method used

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  • Epoxy composite propellant, preparation method and application thereof
  • Epoxy composite propellant, preparation method and application thereof
  • Epoxy composite propellant, preparation method and application thereof

Examples

Experimental program
Comparison scheme
Effect test

preparation example Construction

[0034] The preparation method of above-mentioned epoxy-based composite propellant comprises the following steps:

[0035] Step 1: Weigh and mix the liquid components, the liquid components include epoxy resin, 669 epoxy resin reactive diluent, mix evenly and wait for the bubbles to completely disappear before use;

[0036] Step 2: Weigh and mix the solid components, the solid components include ammonium perchlorate and lead oxide catalyst, mix well and set aside;

[0037] Step 3: Weigh the curing agent. The content of the curing agent is within the range of 3.3-4%. It is determined according to the actual curing demand. In the case of simple drug type and convenient filling, the content of the curing agent can be appropriately increased to speed up the curing speed, and vice versa reduce the content;

[0038] Step 4: Add the curing agent to the liquid component and mix quickly for 5-10 seconds, then add the solid component to the liquid component and stir evenly. The well-mix...

Embodiment 1

[0041] The above-mentioned propellant is processed and made into a solid rocket motor with a diameter of 82mm, and the actual test is carried out, such as figure 1 As shown in section A-A, the diameter of the grain column is 71mm, and it adopts a three-stage variable-section structure with a total length of 700mm. The upper end of the fuel is a circular hole, and the middle section is a circular hole variable-section expansion structure, as shown in figure 1 As shown in the section B-B, the lower end of the fuel is a star-shaped hole, and the epoxy resin mixed filler is used between the three sections of the grain for flame retardancy.

[0042] Such as figure 2 As shown, the engine is made of aluminum casing, the nozzle and plug are made of Bakelite, the throat lining is made of graphite, and there is a 2mm thick phenolic cloth pipe insulation layer outside the fuel powder column.

[0043] KNO is used in the test 3 , Mg, Al mixed ignition powder is ignited, the design ignit...

Embodiment 2

[0047] The above-mentioned propellant was processed to make a 55mm diameter solid rocket motor, and the actual test was carried out. Such as Figure 4 As shown in section A-A, the grain diameter is 46mm, adopts four-stage structure, and the total length is 440mm, such as Figure 4 As shown in section B-B, the upper end of the fuel is a circular hole with a flesh thickness of 14mm.

[0048] Such as Figure 5 As shown, the engine is made of aluminum casing, the nozzle and plug are made of Bakelite, the throat lining is made of graphite, and there is a 2mm thick phenolic cloth pipe insulation layer outside the fuel powder column.

[0049] During the test, the ignition powder mixed with KNO3, Mg and Al was used for ignition, the design ignition pressure was 2MPa, and the pressure was measured at the plug (that is, the upper end of the fuel), and the following results were obtained: Image 6 In the stagnation pressure and thrust curve shown in the figure, a buffer tube and a press...

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Abstract

The invention discloses an epoxy composite propellant, a preparation method and application thereof, belongs to the field of solid rocket fuels, overcomes the defects in the prior art, reduces the fuel processing difficulty and processing cost, and the epoxy composite propellant is applied to a solid rocket engine, and can improve the internal ballistic performance. The epoxy composite propellant is composed of the following components by mass percentage: 75% of ammonium perchlorate, 6.5% of a 669 epoxy resin reactive diluent, 0.25% of a catalyst, 3.3%-4% of a curing agent and the balance epoxy resin. Compared with most standard composite propellants, the composite propellant provided by the invention does not need to add a bonding agent to prevent AP threshing, the production process is simplified, the material has good mechanical properties and high strength, embrittlement is not likely to happen at the low temperature, and a supporting structure does not need to be designed or can be simplified when the composite propellant is applied to a rocket engine with high overload.

Description

technical field [0001] The invention belongs to the field of solid rocket fuel, and in particular relates to an epoxy-based composite propellant, a preparation method and an application thereof. Background technique [0002] When designing rockets, propellants that have been finalized and produced are generally selected, including three categories: double-base propellants, modified double-base propellants, and composite propellants. [0003] Existing small and medium-sized solid rocket motors mostly use double-base propellants or modified double-base propellants, such as double-cobalt-2, double-lead-2, etc., and the processing method is extrusion molding at high temperature, which is difficult to process such as variable cross-section structures Such complex drug types are difficult to manufacture and prone to danger, and there have been many vicious explosion accidents. Moreover, the long-term storage of double-base propellants is poor, and part of the additives and liquid...

Claims

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Application Information

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IPC IPC(8): C06B29/22C06B23/00C06D5/00C06D5/10
CPCC06B23/00C06B29/22C06D5/00C06D5/10
Inventor 石仲仑白澔烔马天任
Owner 石仲仑
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